53030 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

MD Helicopters Inc.: Docket No. FAA–2015– 

3659; Directorate Identifier 2014–SW– 

050–AD. 

(a) Applicability 

This AD applies to Model 369A, 

369D, 369E, 369FF, 369HE, 369HM, 

369HS, 500N, and 600N helicopters 

with an Aerometals main rotor blade 

attach pin (pin) part number (P/N) 

369X1004–5 installed, certificated in 

any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition 

as a pin remaining in service beyond its 

fatigue life. This condition could result 

in failure of a pin, loss of a main rotor 

blade, and subsequent loss of control of 

the helicopter. 

(c) Comments Due Date 

We must receive comments by 

November 2, 2015. 

(d) Compliance 

You are responsible for performing 

each action required by this AD within 

the specified compliance time unless it 

has already been accomplished prior to 

that time. 

(e) Required Actions 

(1) Within 100 hours time-in-service 

(TIS) or during the next annual 

inspection, whichever occurs first: 

(i) Review the maintenance records 

and determine the hours TIS of each pin 

P/N 369X1004–5 and whether there is a 

pin life limit listed in the Airworthiness 

Limitations Section of the applicable 

maintenance manual or Instructions for 

Continued Airworthiness (ICA). If the 

hours TIS on a pin is unknown, remove 

the pin from service. 

(ii) For Model 369A, 369HE, 369HM, 

and 369HS helicopters, if there is no pin 

life limit, establish a new life limit of 

5,760 hours TIS for each pin P/N 

369X1004–5 by making pen-and-ink 

changes or by inserting a copy of this 

AD into the Airworthiness Limitations 

Section of the maintenance manual or 

the ICA. Remove from service any pin 

that has 5,760 or more hours TIS. 

(iii) For Model 369D, 369E, 369FF, 

500N, and 600N helicopters, if there is 

no pin life limit, establish a new life 

limit of 7,600 hours TIS for each pin P/ 

N 369X1004–5 by making pen-and-ink 

changes or by inserting a copy of this 

AD into the Airworthiness Limitations 

Section of the maintenance manual or 

the ICA. Remove from service any pin 

that has 7,600 or more hours TIS. 

(iv) For all model helicopters, add the 

following statement to the 

Airworthiness Limitations Section of 

the maintenance manual or the ICA by 

making pen-and-ink changes or by 

inserting a copy of this AD: If 

interchanged between different model 

helicopters, the life limit of pin P/N 

369X1004–5 must be restricted to the 

lowest life limit indicated for the 

helicopter models and serial numbers 

affected. 

(2) Do not install a pin P/N 

369X1004–5 on any helicopter before 

the requirements of this AD have been 

accomplished. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal 

to: Galib Abumeri, Aviation Safety 

Engineer, Transport Airplane 

Directorate, FAA, 3960 Paramount 

Blvd., Lakewood, California 90712; 

telephone (562) 627–5324 or email at 9- 

ANM-LAACO-AMOCREQUESTS@faa.gov. 

(2) For operations conducted under a 

14 CFR part 119 operating certificate or 

under 14 CFR part 91, subpart K, we 

suggest that you notify your principal 

inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office or certificate 

holding district office before operating 

any aircraft complying with this AD 

through an AMOC. 

(g) Additional Information 

Aerometals Service Bulletin Aero– 

SB–1103, dated July 2, 2014, and 

Aerometals Aero–ICA–101 

Supplemental Instructions for 

Continued Airworthiness, Revision NC, 

dated May 22, 2014, which are not 

incorporated by reference, contain 

additional information about the subject 

of this AD. For service information 

identified in this AD, contact 

Aerometals, 3920 Sandstone Dr., El 

Dorado Hills, CA 95762, telephone (916) 

939–6888, fax (916) 939–6555, 

www.aerometals.aero. You may review 

a copy of information at the FAA, Office 

of the Regional Counsel, Southwest 

Region, 10101 Hillwood Pkwy, Room 

6N–321, Fort Worth, TX 76177. 

(h) Subject 

Joint Aircraft Service Component 

(JASC) Code: 6210 Main Rotor Blades. 

Issued in Fort Worth, Texas, on August 21, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21680 Filed 9–1–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3658; Directorate 

Identifier 2014–SW–039–AD] 

RIN 2120–AA64 

Airworthiness Directives; MD 

Helicopters Inc. (MDHI) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

MDHI Model 369A (Army OH–6A), 

369H, 369HE, 369HM, 369HS, 369D, 

369E, 369F, 369FF, and 500N 

helicopters. This proposed AD would 

require inspecting the auxiliary fuel 

pump (fuel pump) wire routing in the 

left-hand fuel cell and corrective action, 

if necessary. This proposed AD would 

also require installing a warning decal 

on the left-hand fuel cell access cover. 

This proposed AD is prompted by 

accidents resulting from incorrectly 

positioned fuel pump wiring within the 

fuel tank interfering with the operation 

of the fuel quantity sensor float, which 

caused an erroneous fuel quantity 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 53031 

indication in the cockpit. The proposed 

actions are intended to detect and 

correct routing of the fuel pump wiring 

to prevent interference with the fuel 

quantity sensor float, an erroneous fuel 

quantity indication in the cockpit, and 

subsequent fuel exhaustion and 

emergency landing. 

DATES: We must receive comments on 

this proposed AD by November 2, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

economic evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

For service information identified in 

this proposed AD, contact MD 

Helicopters, Inc., Attn: Customer 

Support Division, 4555 E. McDowell 

Rd., Mail Stop M615, Mesa, AZ 85215– 

9734; telephone 1–800–388–3378; fax 

480–346–6813; or at http:// 

www.mdhelicopters.com. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, Texas 76177. 

FOR FURTHER INFORMATION CONTACT: 

Danny Nguyen, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, 

California 90712; telephone (562) 627– 

5247; email danny.nguyen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

We propose to adopt a new AD for 

certain MDHI Model 369A (Army OH– 

6A), 369H, 369HE, 369HM, 369HS, 

369D, 369E, 369F, 369FF, and 500N 

helicopters. This proposed AD would 

require inspecting the routing of the fuel 

pump wiring to determine whether the 

fuel pump wire is properly wrapped 

around the fuel inlet hose and 

correcting the routing of the wiring if it 

is not. This proposed AD would also 

require installing a decal regarding 

correct installation of the fuel pump 

wiring. This proposed AD is prompted 

by two accidents and one incident that 

occurred on Model 369D helicopters 

resulting from an incorrectly positioned 

fuel pump wire within the fuel tank 

interfering with the operation of the fuel 

quantity sensor float, which caused an 

erroneous fuel quantity reading in the 

cockpit. Because the fuel pump is 

installed on all the affected model 

helicopters, we are including them in 

the applicability. According to MDHI, 

because maintenance personnel caused 

the incorrect wire routing by failing to 

follow procedures for installing the fuel 

pump, it is also necessary to install a 

decal on the left-hand fuel cell access 

cover to refer maintenance personnel to 

the appropriate manual procedures. The 

proposed actions are intended to detect 

and correct routing of the fuel pump 

wiring to prevent interference with the 

fuel quantity sensor float, an erroneous 

fuel quantity indication in the cockpit, 

and subsequent fuel exhaustion and 

emergency landing. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs. 

Related Service Information Under 1 

CFR Part 51 

MDHI issued one Service Bulletin on 

April 30, 2014, with five different 

numbers: SB369H–255, SB369E–111, 

SB500N–049, SB369D–213, and 

SB369F–098. The service bulletin 

specifies a one-time inspection of the 

routing of the fuel pump wire in the lefthand fuel cell and corrective action, if 

necessary. The service bulletin also 

specifies installing a warning decal on 

the left-hand fuel cell access cover that 

refers personnel to the procedures for 

routing the fuel pump wire that is 

contained in the appropriate 

maintenance manual. The service 

bulletin states that recent field incidents 

have occurred where maintenance 

personnel have not followed the 

procedures for installation of the fuel 

pump. Also, the service bulletin states 

that an incorrectly installed fuel pump 

wire can interfere with the fuel quantity 

sensor float, which can result in 

erroneous fuel quantity indications. To 

prevent this situation, the service 

information states that the fuel pump 

wire must be wrapped around the fuel 

inlet hose as shown in the applicable 

maintenance manual. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this NPRM. 

Proposed AD Requirements 

This proposed AD would require, 

within 100 hours time-in-service: 

• Removing the fuel quantity sensor 

and, using a mirror and light, inspecting 

to determine whether the fuel pump 

wire is wrapped around the left-hand 

fuel cell fuel inlet hose assembly a 

minimum of one revolution. 

Æ If the fuel pump wire is correctly 

wrapped around the left-hand fuel cell 

fuel inlet hose, installing the fuel 

quantity sensor and performing a fuel 

quantity sensor functional test for 

proper fuel float arm function. 

Æ If the fuel pump wire is not 

correctly wrapped around the left-hand 

fuel cell fuel inlet hose, reinstalling the 

fuel quantity sensor, routing the fuel 

pump wire around the left-hand fuel 

cell fuel inlet hose, and performing a 


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53032 Federal Register / Vol. 80, No. 170 / Wednesday, September 2, 2015 / Proposed Rules 

fuel quantity sensor functional test for 

proper fuel float arm function. 

• Installing a warning decal 

referencing the fuel pump installation 

procedures. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 833 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per hour. Inspecting the fuel 

pump wire routing and installing a 

decal would take 3 hours, and parts 

would cost $20 for a total cost of $275 

per helicopter and $229,075 for the U.S. 

fleet. If required, rerouting the wiring 

would require 1 work-hour for a total 

cost of $85 per helicopter. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by Reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

MD Helicopters Inc.: Docket No. FAA–2015– 

3658; Directorate Identifier 2014–SW– 

039–AD. 

(a) Applicability 

This AD applies to the following 

helicopters, certificated in any category: (1) 

Model 369A (Army OH–6A), 369H, 369HE, 

369HM, 369HS, and 369D; 

(2) Model 369E with a serial number (S/N) 

0001E through 0620E; 

(3) Model 369F and 369FF with a S/N 

0001FF through 0212FF, 0600FF, 0601FF, 

0602FF, and 0700FF through 0711FF) and 

with an auxiliary fuel pump part number 

(P/N) 369A8143–3 installed; and 

(4) Model 500N (S/N LN001 through 

LN0111). 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

incorrect routing of the auxiliary fuel pump 

(fuel pump) wiring. This condition could 

result in an erroneous fuel quantity 

indication in the cockpit and subsequent fuel 

exhaustion and emergency landing. 

(c) Comments Due Date 

We must receive comments by November 

2, 2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

Within 100 hours time-in-service: 

(1) Remove the fuel quantity sensor by 

following the Accomplishment Instructions, 

paragraph 2.B., of MD Helicopters Service 

Bulletin SB369H–255/SB369E111/SB500N– 

049/SB369D–213/SB369F–098, dated April 

30, 2014 (SB). Using a mirror and light, 

inspect the routing of the fuel pump wire in 

the area depicted in Figure 2 of the SB and 

determine whether the fuel pump wire is 

wrapped around the left-hand fuel cell fuel 

inlet hose assembly a minimum of one 

revolution. 

(i) If the fuel pump wire is wrapped around 

the left-hand fuel cell fuel inlet hose a 

minimum of one revolution, install the fuel 

quantity sensor and perform a fuel quantity 

sensor functional test for proper fuel float 

arm function. 

(ii) If the fuel pump wire is not wrapped 

around the left-hand fuel cell fuel inlet hose 

a minimum of one revolution, install the fuel 

quantity sensor, route the fuel pump wire 

around the left-hand fuel cell fuel inlet hose 

by following paragraphs 2.E.(1) through 

2.E.(8) of the SB, and perform a fuel quantity 

sensor functional test for proper fuel float 

arm function. 

(2) Install start pump warning decal, P/N 

MHS5861–66 or equivalent, on the left-hand 

fuel cell cover by following paragraph 2.G. of 

the SB. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Los Angeles Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Danny Nguyen, Aerospace Engineer 

Transport Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, California 

90712; telephone (562) 627–5247; email 9- 

ANM-LAACO-AMOC-REQUESTS@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2840 Fuel Quantity Indicating System. 

Issued in Fort Worth, Texas, on August 21, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–21686 Filed 9–1–15; 8:45 am] 

BILLING CODE 4910–13–P 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS